Evektor EV-97 teamEUROSTAR UK Owner's manual

LIGHT SPORT AVIATION
EV-97 teamEUROSTAR UK

POH/EUR/01 Issue 3 Page 2 of 41
PILOT’S OPERATING HANDBOOK FOR MICROLIGHT AEROPLANE
EV-97 teamEurostar UK
Model: .............................................
Registration: ..............................................
Serial No. ..............................................
Approved by: ...........................................................
This aeroplane must be operated in compliance with the
information and limitations contained herein.
This POH must be available on
board the aeroplane.
WARNING
This aeroplane is not fitted with a certified engine. A power failure
can occur at any time. Never fly over any area on to which a safe
landing cannot be made in the event of an engine failure.

POH/EUR/01 Issue 3 Page 3 of 41
Amendment Record
Issue
Details of Change
Date
Authorised
1
Initial issue
14/07/03
2
Addition of optional hourmeter and warning
lamp –P37
16/8/04
3
CHT Changes –Pages 10, 11, 14
06/06/11

POH/EUR/01 Issue 3 Page 4 of 41
Table of Contents
SECTION 1 –GENERAL INFORMATION AND TECHNICAL DATA ............................6
1.1 Introduction ................................................................................................................................6
1.2 Certification basis.......................................................................................................................6
1.3 Warnings, cautions and notes....................................................................................................6
1.4 Descriptive Data..........................................................................................................................6
SECTION 2 - LIMITATIONS.................................................................................................9
2.1 Introduction ................................................................................................................................9
2.2 Airspeed.......................................................................................................................................9
2.3 Airspeed indicator markings.....................................................................................................9
2.4 Powerplant ................................................................................................................................10
2.5 Powerplant Instrument Markings ..........................................................................................11
2.6 Miscellaneous instrument markings.......................................................................................11
2.7 Weight........................................................................................................................................11
2.8 Centre of Gravity......................................................................................................................11
2.9 Approved manoeuvres .............................................................................................................12
2.10 Manoeuvring Load Factor.....................................................................................................12
2.11 Crew.........................................................................................................................................13
2.12 Kind of Operations.................................................................................................................13
2.13 Fuel ..........................................................................................................................................13
2.14 Maximum Passenger Seating.................................................................................................13
2.15 Other Limitations...................................................................................................................13
2.16 Limitations Placards ..............................................................................................................14
SECTION 3 - EMERGENCIES............................................................................................16
3.1 Introduction ..............................................................................................................................16
3.2 Engine failure............................................................................................................................16
3.3 In-Flight start............................................................................................................................17
3.4 Smoke and fire..........................................................................................................................17
3.5 Glide...........................................................................................................................................18
3.6 Emergency Landings................................................................................................................18
3.7 Precautionary landing..............................................................................................................18
3.8 Landing with a flat tyre ...........................................................................................................19
3.9 Landing with a defective landing gear....................................................................................19
3.10 Recovery from unintentional spin.........................................................................................19
3.11 Other emergencies..................................................................................................................19
SECTION 4 –NORMAL OPERATIONS.............................................................................21
4.1 Introduction ..............................................................................................................................21
4.2 Assembly and disassembly.......................................................................................................21
4.3 Pre-flight inspection .................................................................................................................21

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4.4 Normal procedures...................................................................................................................23
SECTION 5 - PERFORMANCE ..........................................................................................28
5.1 Introduction ..............................................................................................................................28
5.2 Airspeed Indicator System Calibration..................................................................................28
5.3 Stall Speeds ...............................................................................................................................29
5.4 Take-off performance ..............................................................................................................29
5.5 Landing distances.....................................................................................................................29
5.6 Climb performance ..................................................................................................................30
5.7 Cruise.........................................................................................................................................30
5.8 Horizontal Speeds.....................................................................................................................31
5.9 Endurance.................................................................................................................................31
5.10 Baulked landing climb ...........................................................................................................32
5.11 Environmental Effects on Flight Performance and Characteristics..................................32
5.12 Demonstrated crosswind performance.................................................................................32
5.13 Ceiling......................................................................................................................................32
SECTION 6 –WEIGHT AND BALANCE...........................................................................33
6.1 Introduction ..............................................................................................................................33
6.2 Permitted Cockpit Loads.........................................................................................................33
SECTION 7 - AEROPLANE AND SYSTEMS DESCRIPTION.........................................34
7.1 Introduction ..............................................................................................................................34
7.2 Airframe....................................................................................................................................34
7.3 Cockpit Controls.......................................................................................................................35
7.4 Landing gear.............................................................................................................................35
7.5 Seats and safety belts................................................................................................................35
7.6 Baggage compartment..............................................................................................................35
7.7 Canopy.......................................................................................................................................36
7.8 Powerplant ................................................................................................................................36
7.9 Fuel system................................................................................................................................36
7.10 Electrical system.....................................................................................................................37
7.11 Pitot and Static Pressure Systems.........................................................................................38
SECTION 8 - AEROPLANE GROUND HANDLING AND MAINTENANCE. ...............39
8.1 Introduction ..............................................................................................................................39
8.2 Aircraft inspection periods......................................................................................................39
8.3 Aircraft alterations or repairs.................................................................................................39
8.4 Ground handling / Road transport.........................................................................................39
8.5 Cleaning and care.....................................................................................................................41

POH/EUR/01 Issue 3 Page 6 of 41
SECTION 1 –GENERAL INFORMATION AND TECHNICAL DATA
1.1 Introduction
This Pilot’s Operating Handbook has been prepared to provide pilots and
instructors with information for the safe and efficient operation of the EV-97
teamEUROSTAR UK microlight aeroplane. It also contains supplemental data
which may be found useful.
1.2 Certification basis
The EV-97 teamEUROSTAR UK has been approved by UK Civil Aviation Authority
against the requirements of BCAR section S.
1.3 Warnings, cautions and notes
The following definitions apply to warnings, cautions and notes in the flight manual:
WARNING
Means that the non-observation of the corresponding procedure leads to an
immediate or significant degradation of the flight safety.
CAUTION
Means that the non-observation of the corresponding procedure leads to a
minor or possible long term degradation of the flight safety.
NOTE
Draws attention to any special item not directly related to safety, but which is
important or unusual.
1.4 Descriptive Data
1.4.1 Aircraft description
EV-97 teamEurostar UK is an aircraft intended for recreational and touring flying and
is limited to non-aerobatic operations in Visual Meteorological Conditions(VMC). It is a
single engine, all metal, low-wing monoplane of semi-monocoque construction with two
side-by-side seats. The aeroplane is equipped with a fixed tricycle undercarriage with a
steerable nose wheel.
The powerplant is a ROTAX 912 (80 hp), four cylinder, four stroke engine driving a two
blade V230C, fixed wooden propeller (standard propeller). An alternative GT 166 x 145
fixed pitch wooden propeller may also be fitted. The engine is fitted with a gearbox
having a reduction ratio of 2.27:1.

POH/EUR/01 Issue 3 Page 7 of 41
1.4.2 Technical Data
Wing
Span 8.1 m 26.57 ft
Area 9.84 m2105.92 ft2
Mean Aerodynamic Centre (MAC) 1.25 m 4.10 ft
Wing Loading 45.7 kg/m29.37 lb/ft2
Aileron area 0.21 m22.26 ft2
Flap area 0.52 m2 5.60 ft2
Fuselage
Length 5.98 m 19.62 ft
Width 1.04 m 3.41 ft
Height 2.34 m 7.67 ft
Horizontal tail unit
Span 2.5 m 8.20 ft
Area 1.95 m2 20.99 ft2
Elevator area 0.8 m28.60 ft2
Vertical tail unit
Height 1.24 m 4.07 ft
Area 1.0 m210.76 ft2
Rudder area 0.4 m24.30 ft2
Landing gear
Wheel track 1.6 m 5.25 ft
Wheel base 1.35 m 4.42 ft
Main wheel diameter 350 mm 14 in
Nose wheel diameter 350 mm 14 in

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1.4.3 Three-view drawing
8 .1 m
2 6 .5 7 f t
2 .5 m
8 . 2 f t
2.34m
7.7ft
19.62 ft
5.98 m
2 .2 5 m
7 .3 8 f t
0 .9 4 m
3 . 1 f t
4.42 ft
1.35 m 1.6 m
5.25 ft
3.42 ft
1.04 m

POH/EUR/01 Issue 3 Page 9 of 41
SECTION 2 - LIMITATIONS
2.1 Introduction
Section 2 includes operating limitations, instrument markings and basic placards
necessary for the safe operation of the aircraft, its engine, standard systems and
standard equipment.
2.2 Airspeed
Airspeed limitations and their operational significances are shown below:
Speed
IAS
mph
Remarks
VNE
Never exceed
speed
146
Do not exceed this speed in
any operation.
VA
Manoeuvring
speed
100
Do not make full or abrupt
control movement above
this speed, because under
certain conditions the
aircraft may be overstressed
by full control movement.
VNO
Maximum
structural
cruising speed
118
Do not exceed this speed
except in smooth air, and then
only with caution.
VFE
Maximum Flap.
Extending speed
77
Do not exceed this speed with
flaps extended.
2.3 Airspeed indicator markings
Airspeed indicator markings and their colour-code significances are shown
below:
Marking
IAS value or range
mph
Significance
White
arc
40 –77
Positive Flap Operating Range.
Green
arc
49 –118
Normal Operating Range.
Yellow
arc
118 –146
Manoeuvres must be conducted
with caution and only in smooth
air.
Red
line
146
Maximum speed for all operations.
The lower end of the white arc is 1.1 VSO
The lower end of the green arc is 1.1 VS1

POH/EUR/01 Issue 3 Page 10 of 41
2.4 Powerplant
Engine Model:
ROTAX 912 UL
Engine Manufacturer:
Bombardier-Rotax GMBH
P
o
w
e
r
Max Take-off:
59.6 kW / 80 hp at 5800 rpm, max.5 minutes
Max.
Continuous:
56 kW / 75 hp at 5200 rpm
Cruising:
53 kW / 71 hp at 4800 rpm
E
n
g
i
n
e
s
p
e
e
d
Max. Take-off:
5800 rpm, max. 5 min.
Max.
Continuous:
5200 rpm
Cruising:
4800 rpm
Idling:
~1400 rpm
Cylinder
head
temp.
Minimum
60 °C
140 °F
Maximum
150 °C (120 °C*)
302 °F (248 °F*)
Oil temp.
Minimum
50 °C
122 °F
Maximum
140 °C
284 °F
Optimum
90 –110 °C
194 - 230°F
Oil
pressure
Maximum
7,0 bar
Minimum:
1,5 bar
Optimum:
1,5-4,0 bar
Fuel:
see 2.13
Fuel Pressure
min. 0.15 bar, max. 0.4 bar
Oil:
Automotive engine oil of registered brand with gear
additives, but not aircraft oil (refer to engine Operator´s
Manual).
API classification SF or SG.
Propellers and
Manufacturers
V 230C
VZLÚ
Praha,
Czech Republic
GT-2/166/VSR FW101 SRTC
GT Propellers
Riccione
Italy
Types:
Two blade fixed
wooden propeller
Two blade fixed wooden
propeller
Propeller diameters:
1625 mm
1660 mm
Propeller pitches:
18°20´ - 18°55´
1450 mm
WARNING
The Rotax 912 UL has not been certified as an aircraft engine and its failure may occur at
any time. The pilot is fully responsible for consequences of such a failure. Never fly over
an area on to which you cannot safely land in the event of an engine failure.
* If 50/50 ethylene glycol/water coolant is used and if Service
Bulletin SB/EUR/006 Issue 1 is complied with.

POH/EUR/01 Issue 3 Page 11 of 41
2.5 Powerplant Instrument Markings
Analogue powerplant instruments are installed in the EV-97 teamEurostar UK
aeroplane, with the following markings:
Minimum
Limit
Normal
Operating
Caution Range
Maximum Range
Engine speed (RPM)
1400
1400-5200
5200-5800
5800
Cylinder Head Temperature
(CHT)
60 °C, 140 °F
60-100 °C
140-212 °F
100-150 °C, 212-302 °F
100-120 °C, 212-248 °F*
150 °C, 302 °F
120 °C, 248 °F*
Oil Temperature
50 °C
122 °F
90-110 °C
194-230 °F
50-90 °C, 122-194 °F
110-140 °C, 230-284 °F
140 °C
284 °F
Oil Pressure
1.5 bar
1.5 - 4.0
bar
4.0 - 5.0 bar
7.0 bar
cold engine starting
Fuel Pressure
0.15 bar
0.2 –0.3
bar
0.3 –0.4 bar
0.4 bar
* If 50/50 ethylene glycol/water coolant is used and if Service Bulletin SB/EUR/006 Issue 1 is complied with.
2.6 Miscellaneous instrument markings
Fuel gauge
A fuel reserve of 11 litres (2.42 Imp. gals) is indicated by yellow warning lamp.
2.7 Weight
Empty weight (standard equipment) max. 268 kg 591 lbs
NOTE
Actual empty weight is stated in SECTION 6, par. 6.2
Max. take-off weight 450kg 992 lbs
Max landing weight 450kg 992 lbs
Max. weight of fuel 47kg 104 lbs
Max. baggage weight 15kg 33 lbs
2.8 Centre of Gravity
Empty aircraft C.G. position (standard) 18±2% MAC = 200 –250 mm AOD
Operating C.G. range 20-34% MAC = 250 –425 mm AOD
Datum is wing leading edge.

POH/EUR/01 Issue 3 Page 12 of 41
2.9 Approved manoeuvres
Aeroplane Category: Normal; the EV-97 teamEurostar UK aeroplane is approved
for normal and below listed manoeuvres:
Steep turns not exceeding 60° bank
Lazy eights
Chandelles
Stalls (except whip stalls) WARNING
Aerobatics and intentional spins are prohibited !
2.10 Manoeuvring Load Factor
L O A D F A C T O R [ - ]
0
1 0
V
V
V
V
S 0
S 1
A
N E
2 0
3 0
4 0
5 0
6 0
7 0
8 0
9 0
100
1 1 0
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
-1 -2 1 2 3 4
0
1 0
2 0
3 0
4 0
5 0
6 0
7 0
8 0
9 0
1 0 0
1 1 0
1 2 0
1 3 0
1 4 0
1 5 0
1 6 0
1 7 0
1 8 0
0
1 0
2 0
3 0
4 0
5 0
6 0
7 0
8 0
9 0
1 0 0
1 1 0
1 2 0
1 3 0
1 4 0
1 5 0
1 6 0
1 7 0
1 9 0
KIAS
IAS [km/h]
IAS [mph]
EV-97 EUROSTAR FLIGHT ENVELOPE
A
GE
D

POH/EUR/01 Issue 3 Page 13 of 41
2.11 Crew
Minimum Crew 1
Minimum Crew Weight 55 kg, 121 lb
Maximum Crew Weight see 6.2
WARNING
Always comply with the maximum take-off weight of 450 kg (992 lbs)
2.12 Kind of Operations
Daytime VFR flights only.
WARNING
IFR flights and flights under icing conditions are prohibited.
Minimum instruments required for VFR flights:
(i) Airspeed indicator, marked in accordance with 2.3
(ii) Altimeter
(iii) Magnetic compass
(iv) Slip ball
2.13 Fuel
Regular or premium unleaded automobile fuel to EN228, minimum RON
90.
AVGAS 100LL. The higher lead content in AVGAS can result in wear of
valve seats and increased combustion chamber deposits. Use AVGAS only
if other fuels are not available.
For other suitable fuel types, refer to the engine Operator’s Manual.
Fuel tank volume 65 litres 14.3 Imp. gals.
Unusable fuel quantity 2.9 litres 0.64 Imp. gals.
2.14 Maximum Passenger Seating
Number of seats 2
2.15 Other Limitations
Smoking is not permitted on board.

POH/EUR/01 Issue 3 Page 14 of 41
2.16 Limitations Placards
The owner of this aeroplane is responsible for the readability of placards during
the aircraft service life.
The following placards are located on the aeroplane:
In view of the pilot:
Flight limited to daytime VFR non-icing conditions.
Aerobatics and intentional spinning are prohibited. This
microlight aeroplane has not been approved to an
internationally recognised airworthiness standard.
AIRSPEEDS (IAS)
VNE (Never exceed speed) 146 mph
VA (Maximum manoeuvring speed) 100 mph
VFE (Flaps extended max. speed) 77 mph
VS (Stall speed, flaps extended) 36 mph
ENGINE LIMITATIONS
Maximum take-off (max. 5 minutes) 5800 rpm
Max. continuous 5200 rpm
Idle approx. 1400 rpm
Max. CHT 150ºC or 120ºC*
Max. oil temp. 140ºC
Min. oil temp. 50ºC
Min. oil pressure 1.5 bar
Max. oil pressure 7.0 bar
Minimum fuel pressure 0.15 bar
Maximum fuel pressure 0.4 bar
* If 50/50 ethylene glycol/water coolant is used and if Service Bulletin SB/EUR/006 Issue 1 is complied with.
FUEL and LOAD LIMITS
Capacity 65 litres
Unusable fuel 2.9 litres
Maximum take-off weight 450 kg
Max. empty weight 268 kg
Actual empty weight ___ kg
Max. baggage weight 15 kg
Minimum Cockpit Load 55 kg
Cockpit Load incl. Baggage (kg)
Max. Fuel Load (litres)
172 (maximum)
14
160
31
150
44
140
58
135 or less
Full fuel

POH/EUR/01 Issue 3 Page 15 of 41
NOTE
The values stated on the above placard, FUEL and LOAD LIMITS, are valid for the
maximum permitted empty weight of the aircraft. If the empty weight is less than the
maximum of 268 kg, a customised placard may be used for revised load limits.
CG Limits
Operating C.G. range: 250 –425 mm AOD
Datum is wing leading edge.
In the baggage area:
In view of both occupants:
Adjacent to the fuel filler:
BAGGAGE
MAX.
15 kg
NO
SMOKING
90 RON minimum MOGAS unleaded to EN 228;
or AVGAS 100LL*
Prolonged use of AVGAS 100LL should be avoided.

POH/EUR/01 Issue 3 Page 16 of 41
SECTION 3 - EMERGENCIES
3.1 Introduction
Section 3 provides checklists and detailed procedures for coping with various
emergencies that may occur. Emergencies caused by aircraft or engine
malfunction are extremely rare if proper pre-flight inspections and maintenance are
practiced.
However, should an emergency arise, the basic guidelines described in this section
should be considered and applied as necessary to correct the problem. It is
normally impractical to refer to this manual after the emergency has arisen; for this
reason, pilots are strongly advised to familiarise themselves with its contents before
flight.
3.2 Engine failure
Engine failure during take-off run:
1. Throttle - decrease to idle
2. Ignition - switch off
3. Brake - firmly as required
Engine failure during take-off:
1. Speed - glide at 68 mph.
2. Altitude - below 160 ft (50 m): land in take-off direction.
- over 160 ft (50 m): choose landing area.
3. Wind - find direction and velocity.
4. Landing area - choose free area without obstacles; check for cables.
5. Flaps - extend as needed.
6. Fuel cock - shut off.
7. Ignition - switch off.
8. Propeller - set to the horizontal position by means of starter.
9. Safety harness- tighten.
10. Master switch - switch off before landing.
NOTE
Skip 6-10 if necessary. In an emergency, the pilot’s priority is to land safely.
Engine failure in flight:
1. Speed - glide at 68 mph
2. Altitude - below 160 ft (50 m): land in flight direction
- over 160 ft (50 m): choose landing area
3. Wind - evaluate direction and velocity
4. Landing area - choose free area without obstacles
5. Flaps - extend if necessary
6. Fuel cock - shut off
7. Ignition - switch off
8. Propeller - set to the horizontal position by means of starter
9. Safety harness- tighten
10. Master switch - switch off before landing
11. Land

POH/EUR/01 Issue 3 Page 17 of 41
3.3 In-Flight start
1. Speed - glide at 68 mph
2. Altitude - check
3. Landing area - choose according to altitude
4. Master switch - switch on
5. Fuel cock - open
6. Choke - as necessary (for cold engine)
7. Throttle - set 1/3 open
8. Ignition - switch on
9. Starter - push button to start the engine
If the engine cannot be started due to a flat battery, and there is adequate height,
increase the flight speed to 124 mph so that air flow can rotate the propeller, thus
enabling the engine to start.
WARNING
The loss of altitude during in-flight engine starting is about 1300 ft
and must be taken into consideration.
3.4 Smoke and fire
3.4.1 Fire on the ground:
1. Fuel cock - shut off
2. Throttle - fully open
3. Master switch - switch off
4. Ignition - switch off
5. Abandon the aeroplane
Extinguish fire if possible, or call the fire-brigade.
3.4.2 Fire during take-off roll:
1. Abort take-off - brake hard
2. Master switch - switch off
3. Fuel cock - shut off
4. Throttle - fully open until fire stops or engine stops.
5. Ignition - switch off
6. Abandon the aeroplane
Extinguish fire if possible, or call the fire-brigade.
3.4.3 Fire during take-off (climb out):
1. Fuel cock - shut off
2. Throttle - fully open
3. Speed - 62-68 mph
4. Master switch - switch off
5. Ignition - switch off
6. Land and brake
7. Abandon the aeroplane
Extinguish fire if possible, or call the fire-brigade.

POH/EUR/01 Issue 3 Page 18 of 41
3.4.4 Fire in flight:
1. Fuel cock - shut off
2. Throttle - fully open to use excess fuel.
3. Master switch - switch off
4. Ignition - switch off after using up fuel in carburettors and engine
stops.
5. Choose an emergency landing area.
6. Make emergency landing in accordance with 3.5 below.
7. Abandon the aeroplane
Extinguish fire if possible or call the fire-brigade.
NOTE
Estimated time to pump fuel out of carburettors is 30 seconds.
3.5 Glide
In the case of engine failure it is important to know and quickly establish the
conditions for best glide:
1. Speed - ~68 mph
2. Flaps - retracted
3. Instruments - within permitted limits
3.6 Emergency Landings
Emergency landings are generally carried out in the case of engine failure where
the engine cannot be re-started.
1. Best glide angle speed - 68 mph.
2. Trim - trim the aeroplane.
3. Safety harnesses - tighten.
4. Flaps - as needed.
5. MAYDAY - report your location if possible.
6. Fuel cock - shut off.
7. Ignition - switch off.
8. Master switch - switch off.
3.7 Precautionary landing
A precautionary landing is generally carried out in the cases where the pilot may be
disorientated, the aircraft has no fuel reserve, or where bad weather or poor
visibility present severe flight hazards.
1. Determine wind direction, choose landing area.
2. Make a PAN call on the radio and report your plan to land. Also state the
landing area location.
3. Perform low-altitude passage into wind over the right-hand side of the
chosen area with flaps extended to the “TAKE-OFF“ position at a speed of 68
mph to thoroughly inspect the area. Pay particular attention to electricity or
telephone cables running across the landing area; these are often difficult to see.
4. Perform flight around the chosen area.
5. Perform an approach at increased idling with fully extended flaps.
6. Reduce power to idle when over the runway threshold and touch-down at
the start of the chosen area.

POH/EUR/01 Issue 3 Page 19 of 41
7. After stopping the aeroplane switch off all switches, shut off the fuel cock,
lock the aeroplane and look for help.
NOTE
Watch the chosen area permanently during precautionary landing.
3.8 Landing with a flat tyre
1. During the landing hold off, keep the damaged wheel above ground as long
as possible using the ailerons.
2. Maintain direction during the landing roll using firm rudder pressure.
3.9 Landing with a defective landing gear
1. If the main landing gear is damaged, perform touch-down at the lowest
speed possible and attempt to maintain direction during the landing roll.
2. If the nose wheel is damaged, perform touch-down at the lowest speed
possible and hold the nose wheel over a runway using the elevator as long as
possible.
3.10 Recovery from unintentional spin
WARNING
Intentional spins are prohibited! The procedure below is only for information.
The aircraft has no tendency to spontaneously enter an uncontrollable spin if
normal piloting techniques are used.
The following standard procedure can be used to recover from an intentional spin:
1. Throttle - reduced to idle
2. Control stick - ailerons neutralised
3. Rudder pedals - full opposite rudder
4. Control stick - forward, elevator control as required to stop spin.
5.Rudder pedals - immediately after rotation stops, neutralise the
rudder.
6. Recover from the dive, take care not to exceed VNE.
3.11 Other emergencies
3.11.1 Vibration
If any forced aircraft vibrations appear:
1. Adjust the engine speed to the setting at which the vibration is minimum.
2. Land as soon as possible; perform a precautionary landing if necessary.
3.11.2 Carburettor icing
The EV-97 teamEurostar UK is fitted with a coolant carburettor heater system
which should prevent carburettor icing; however icing may be possible under
extreme conditions.
Certain weather conditions, particularly low temperatures and high humidity,
give rise to the risk of carburettor icing. The carburettor icing shows itself
through a decrease in engine power and an increase in engine temperatures.

POH/EUR/01 Issue 3 Page 20 of 41
To recover the engine power, the following procedure is recommended:
1. Speed - 68 mph
2. Throttle- set for 1/3 power
3. If possible, leave the icing area
4. Increase the engine power gradually to cruise conditions after 1-2 minutes.
If engine power cannot be recovered, make a precautionary landing, depending on
the circumstances.